Adjusting device for aeroplanes



e. SCHENKEL. ADJUSTING DEVICE FOR AEROPLANES.

APPUCATION FILED JULY 2, 1920..

Patented Jan. 11,1921.

3 MS Ms W mb v a mu w 4 2 yam GOTTFBIED SGHENKEL, OF WINTERTHUR, SWITZERLAND.

ADJUSTING DEVICE FOR AEROPLANES.

Specification of Letters Patent.

Patented Jan. 11, 1921.

Application filed July 2, 1920. Serial No. 393,702.

To all whom it may concern:

Be it known that I, GOTTFRIED SGHENKEL, a citizen of the Republic of Switzerland, residing at Winterthur, in the Canton of Zurich, Switzerland, have invented an Improved Adjusting Device for Aeroplanes, of which the following is a specification.

This invention has for its object an ad-- ustmg device for aeroplanes and concernsv understood, reference is made to the accompanying drawings, in which Figure 1 shows a cross'sectional view, in diagrammatical form, of this adjusting device in normal position;

Fig. 2 shows a similar view with the device adjusted to obtain a greater convexity of the supporting planes;

Fig. 3 shows a side view of part of the mechanism, and

Fig. 4 is a perspective view of the adjusting device.

In referring to these drawings, I have shown those parts only which are essential to my invention, namel a portion of the aeroplane frame, one o the series of supporting ribs for the supporting planesof the air craft, and the mechanism for causing this and the other similar ribs and the planes attached thereto to be adjusted for the purpose mentioned.

The means for the supporting of the.

planes of the air craft comprise the beams 1 and 1*, and a suitable number of ribs, 2 of aluminium or other metal having stays 3, 4, 5, and 6 which are arranged crosswise and hingedly connected with each other and with the upper and lower portion of the ribs, Of these ribs at least one, that shown in Fig. 4, is fitted with the adjusting device herelnafter described.

The end of the rib 2 adjacent to the stay 3 is provided with a ring-shaped attachment 2 for the reception of the beam 1 which at that part is formed with a flange fitting in saidattachment in such a manner that this end of the rib can swing about the axis of the beam 1. The other end of the rib 2 which is adjacent to the stay 6 is fashioned into an oblong guiding frame 7 for the reception of the beam I this frame being mounted and disposed in such a way that when the adjustment of the ribs 2 and the air craft planes is effected, see Fig. 2, allowance is made for the corresponding bending movement of this end of the rib. The hinge connections of the stays, which latter during the adjustment of the rib are also adjusted in relation to their positions, are indicated at 21, 22 and 23.

The adjusting mechanism consists of rods 8, 9, l0 and 11 mounted parallel to the beams 1 and 1 and supported and guided by guiding members 12, 13, 14 and 15 respectively. These guiding members in turn are mounted between the four sets of stays and suitably attached to such parts thereof which remain stationary relative to one another. Pivotally connected with the rods 8, 9,10, 11, by means of levers 16, 17, 18 and 19, arerotatable shafts 20, the latter being arranged between and at right angles 1 to the beams and bearing therein.

If therefore the aforesaid rods are moved in the direction of the arrows, Fig. 4, or if the shafts are turned, both of which movements may be eflected by any known and convenient appliance (not shown), the levers 16, 17, 18, and 19 are caused to be swung upward into the position indicated in dotted lines in Fig. 3. The consequence is that the rib-end adjacent to the stay 3 is made to swing about the axis of the beam 1 while the other end of the rib, namely that adjacent to the stay 6 is caused to be swung about the axis of the beam 1*, at the same time adjusting itself in the oblong guiding frame 7. The stays, owing to their hinge connections, are also made to adjust themselves and through these movements produce a greater convexity'of the carrying ribs 2 and therefore of the supporting air craft planes secured to the said ribs.

It will be understood that the lower and upper portions of the ribs 2, at or near the points where they are hinged to the stays,

must be made to overlap as shown at 24 and 25 respectively, and any covering at the side of the ribs as also the su porting planes themselves must in a simi ar" manner be constructed of overlapping pieces.

Having now fully described my said invention what I claim and desire'to secure by Letters Patent is In the herein-described adjusting device for the planes of air-craft, the combination, with two beams forming part of the aircraft frame, of a series of ribs mounted parallel to each other and transversely of the said beams, a number of stays hingedly connected with one another and with the upper and lower portions of the ribs, a ring-shaped attachment at one end of the ribs and an oblong guiding frame secured near the other end thereof, the said attachment and frame being adapted to receive the first and second beam respectively, a

guiding member mounted between each set and guided by the said members, a s

of stays of one of the said ribs, rods ar-= and parallel to the beamsranged between haft mounted at either side of each of the ribs and bearing in the beams, and a lever connecting each of the rods with its corresponding shaft, all substantially as and for the purpose set forth. 1

In testimony whereof I have hereunto set my hand in the presence of two subscribing witnesses.

GOTTFRIED SCHENKEL I \Vitnesses J. H. L. LARENTZEN W. L. LANGER. 

